CN109341883B - Total temperature measuring device for aero-engine combustion chamber - Google Patents
Total temperature measuring device for aero-engine combustion chamber Download PDFInfo
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- CN109341883B CN109341883B CN201811252761.0A CN201811252761A CN109341883B CN 109341883 B CN109341883 B CN 109341883B CN 201811252761 A CN201811252761 A CN 201811252761A CN 109341883 B CN109341883 B CN 109341883B
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 34
- 239000000919 ceramic Substances 0.000 claims abstract description 32
- 238000001816 cooling Methods 0.000 claims abstract description 29
- 239000000523 sample Substances 0.000 claims abstract description 29
- 239000002184 metal Substances 0.000 claims abstract description 22
- 229910052751 metal Inorganic materials 0.000 claims abstract description 22
- 238000009434 installation Methods 0.000 claims abstract description 7
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 3
- 239000000498 cooling water Substances 0.000 claims description 24
- 238000009529 body temperature measurement Methods 0.000 claims description 21
- 238000007789 sealing Methods 0.000 claims description 17
- 239000010935 stainless steel Substances 0.000 claims description 10
- 229910001220 stainless steel Inorganic materials 0.000 claims description 10
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052802 copper Inorganic materials 0.000 claims description 3
- 239000010949 copper Substances 0.000 claims description 3
- 238000005498 polishing Methods 0.000 claims 1
- 229910000601 superalloy Inorganic materials 0.000 claims 1
- 238000005259 measurement Methods 0.000 description 10
- 230000005855 radiation Effects 0.000 description 7
- 238000012360 testing method Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- PXXKQOPKNFECSZ-UHFFFAOYSA-N platinum rhodium Chemical compound [Rh].[Pt] PXXKQOPKNFECSZ-UHFFFAOYSA-N 0.000 description 2
- 238000004064 recycling Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000691 measurement method Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 239000013307 optical fiber Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000000041 tunable diode laser absorption spectroscopy Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
- G01K7/02—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples
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- General Physics & Mathematics (AREA)
- Measuring Temperature Or Quantity Of Heat (AREA)
Abstract
The invention discloses an aeroengine combustion chamber total temperature measuring device, which comprises: a mounting base; the temperature measuring rake body is of a strip-shaped structure, one end of the temperature measuring rake body is connected with the mounting base, a plurality of mounting holes with top openings facing the incoming flow direction are formed in the length direction, and a water cooling unit is arranged in the temperature measuring rake body; a plurality of thermocouple probes mounted in the corresponding mounting holes; a thermocouple wire lead-out pipe installed on the installation base for installing a thermocouple wire connected with a thermocouple probe, the thermocouple probe comprising: the metal fixing sleeve is fixedly connected with the mounting hole; the shielding cover ceramic tube is arranged in the metal fixing sleeve and is provided with an air inlet which faces to the top opening and an air outlet which is vertical to the incoming flow direction, and the air outlet is communicated to the outside of the temperature measuring rake main body; thermocouple wires; the invention can obtain the temperature distribution of the combustion chamber, has large temperature measuring range, high temperature measuring precision, long continuous temperature measuring time, easy replacement of the thermocouple probe and low temperature measuring cost.
Description
Technical Field
The invention relates to the technical field of total temperature measurement of aero-engine combustion chambers, in particular to a total temperature measurement device of an aero-engine combustion chamber.
Background
The temperature test under the high-temperature and high-speed condition is very important in the technical field of aerospace, particularly in the model design, development and experiments of aeroengines, and can be used for calculating combustion efficiency, analyzing the temperature distribution of the outlet of a combustion chamber, ensuring the safe work of turbine blades and the like. The measurement of the temperature of high-temperature airflow is a long-standing technical problem because of high temperature, severe environment and many influencing factors.
The total temperature of the high-speed air flow refers to the temperature which can be reached by the air flow in an adiabatic stagnation state, and complete stagnation in the actual measurement process cannot be realized. When high-speed air flows to the measuring device, the total temperature of the high-speed air flows is difficult to measure due to the influences of compression heat and friction heat, and particularly under the high-temperature and high-speed conditions, radiation errors and heat conduction errors are aggravated, and accurate measurement of the total temperature of the high-speed air flows is more difficult.
Some existing advanced measurement methods for measuring the temperature of high-temperature high-speed airflow include: optical fiber type temperature sensor, infrared thermometer, optical pyrometer, TDLAS temperature measurement, etc., but factors influencing measurement accuracy are too many, and equipment measurement accuracy and stability are difficult to meet the requirements of aero-engine, rocket engine and high temperature wind tunnel test accuracy.
At present, a shielding type total temperature thermocouple probe is widely adopted for high-precision measurement of high-temperature and high-speed air flow at home and abroad, is a contact type temperature measuring method, has the characteristics of simplicity, reliability and higher temperature measuring precision, outputs an electric signal, and is convenient for long-distance and multi-point measurement. The existing thermocouple probe temperature measuring rake can measure high-speed air flow at 1600 ℃ of the high-temperature wind tunnel, but the thermocouple probe is easy to burn out and not easy to replace, and the temperature measuring rake is large in size, high in manufacturing cost and high in replacement cost. Aiming at the total temperature measurement requirement of an aeroengine combustion chamber up to 1800 ℃, on one hand, the air flow temperature is high, the radiation error is increased, and a thermocouple is easy to burn out at high temperature and is required to be replaced easily; on the other hand, the engine combustion chamber is compact in structure, the size of the temperature measuring harrow is required to be small, and in order to ensure the strength of the temperature measuring harrow, a cooling structure is required to be designed to sufficiently cool the temperature measuring harrow, and the temperature measuring harrow device which is not disclosed and reported is caused by multiple difficulties. In the prior art, the average temperature of the total incoming flow temperature is obtained by measuring the total incoming flow pressure and flow and reversely calculating by utilizing a jet pipe flow formula, and the temperature distribution of the combustion chamber cannot be obtained.
Disclosure of Invention
The invention provides an aeroengine combustion chamber total temperature measuring device which can measure high-temperature high-speed airflow at 1800 ℃, has the advantages of small temperature measuring rake size, compact structure, long continuous temperature measuring time, easy replacement of thermocouple probes, low temperature measuring cost, reduced radiation error and improved temperature measuring accuracy.
An aeroengine combustion chamber total temperature measurement device, comprising:
A mounting base;
the temperature measuring rake body is of a strip-shaped structure, one end of the temperature measuring rake body is connected with the mounting base, a plurality of mounting holes with top openings facing the incoming flow direction are formed in the length direction, and a water cooling unit is arranged in the temperature measuring rake body;
A plurality of thermocouple probes mounted in the corresponding mounting holes;
A thermocouple wire lead-out pipe installed on the installation base for installing a thermocouple wire connected with a thermocouple probe, the thermocouple probe comprising:
The metal fixing sleeve is fixedly connected with the mounting hole;
The shielding cover ceramic tube is arranged in the metal fixing sleeve and is provided with an air inlet which faces to the top opening and an air outlet which is vertical to the incoming flow direction, and the air outlet is communicated to the outside of the temperature measuring rake main body;
the tail part of the thermocouple wire is in threaded connection with the bottom opening of the mounting hole, and the head part of the thermocouple wire is arranged in the ceramic tube of the shielding cover.
According to the invention, the thermocouple wire is in threaded fit connection with the main body of the temperature measuring rake, so that the thermocouple wire is convenient to assemble and disassemble, the temperature measuring cost is low, the radiation error of the ceramic tube of the shielding cover is reduced, and the accuracy of temperature measurement is improved. Meanwhile, a cooling cavity is arranged in the temperature measuring rake body to cool the temperature measuring rake body.
As the total temperature of the combustion chamber of the aero-engine is high and is an aerobic environment, the temperature measurement limit of the existing thermocouple is reached. The maximum temperature of the platinum-rhodium 30-platinum-rhodium 6 thermocouple can reach 1873K when the thermocouple is used for a long time, the maximum temperature of the thermocouple can reach 2073K when the thermocouple is used for a short time, and the thermocouple is easy to damage in a high-temperature state. In order to reduce the temperature measurement cost, the thermocouple wire is fixed on the temperature measurement rake body through threads and can be replaced independently. When a certain thermocouple on the temperature measuring rake is damaged, the thermocouple is replaced to ensure the recycling of the main body of the temperature measuring rake. Because the structure of temperature measurement harrow main part is complicated, processing cost is high, realizes the reuse of temperature measurement harrow main part can reduce the temperature measurement cost.
In order to obtain the temperature distribution in the combustion chamber of the aeroengine, a plurality of thermocouple probes are arranged on the temperature measuring rake, the number of the probes is determined according to the diameter of a runner, 4 probes are arranged at the diameter of 400-600 mm, 5 probes are arranged at the diameter of more than 600mm, and the positions of the probes are arranged according to equal intervals or equal areas, preferably, the probes are arranged according to equal areas.
The total temperature of a combustion chamber of the general aeroengine is up to 1800 ℃, the air flow speed is high, a plurality of working conditions are tested at one time, the test time is up to 60 seconds, and in order to ensure the strength of a temperature measuring rake, the main body of the temperature measuring rake can bear the impact of high-speed air flow, and preferably, the main body of the temperature measuring rake adopts high-temperature alloy. Further preferably, the temperature measuring rake body adopts 1Cr25Ni20Si2.
In order to improve the cooling effect, preferably, the water-cooling unit includes:
the cooling cavity is a cavity body of the temperature measuring rake body, which is opposite to the flowing direction, extends from the end close to the mounting base to the other end and is provided with a mounting opening;
a back seal cover plate sealing the mounting opening;
one end of the cooling water inlet pipe is arranged on the mounting base, and the other end of the cooling water inlet pipe extends into the cooling cavity and extends to the end far away from the mounting base;
And one end of the cooling water outlet pipe is arranged on the mounting base and is communicated with the cooling cavity.
The effective water-cooling unit is arranged, and the continuous test time of the temperature measuring rake can reach 60s or more. The temperature in the aeroengine combustion chamber is inhomogeneous, and the temperature near the center is high, in order to reach better cooling effect, and the cooling water inlet tube lets in the top of temperature measurement harrow main part (the one end of keeping away from mounting base), and cooling water temperature is low this moment, and the temperature of top harrow body is high, has promoted the heat transfer, absorbs the hot cooling water of harrow body and discharges in outlet pipe department through the cooling chamber.
In order to facilitate disassembly and assembly, preferably, the bottom opening of the mounting hole is communicated with the cooling cavity.
In order to realize the sealing of the cooling cavity, the thermocouple is convenient to replace, the temperature measuring rake back is rectangular in incoming flow direction, the back sealing cover plate and the sealing gasket are fixed on the temperature measuring rake body through screws, and the sealing gasket is a polished copper gasket with the thickness of 0.3-0.5 mm.
In order to ensure enough cooling water flow, the inlet pressure of the cooling water pipe is increased under the condition that the diameter of the cooling water pipe is fixed, and the inlet pressure of the cooling water pipe is not lower than 0.8MPa.
The aeroengine combustion chamber is compact in structure, the space for installing the temperature measuring rake is small, meanwhile, in order to reduce the interference of the temperature measuring rake on a flow field, the size of the temperature measuring rake is required to be small, through fine layout, under the condition of ensuring cooling, the cross section of the main body of the temperature measuring rake is preferably 12-18 mm in the vertical incoming flow direction, and the height of the main body of the temperature measuring rake is 35-40 mm in the incoming flow direction. Meets the installation requirement.
In order to reduce the impact of high-speed gas on the temperature measuring rake and further reduce the interference of the temperature measuring rake on the flow field, preferably, the side surface of the temperature measuring rake body facing the incoming flow direction is in a convex arc shape.
In order to reduce the radiation heat exchange between the thermocouple and the ceramic tube, the temperature of the thermocouple is close to that of the ceramic tube, which reduces the heat conduction from the ceramic tube to the temperature measuring rake body, preferably, a gap of 0.2-0.3 mm is arranged between the ceramic tube of the shielding cover and the metal fixing sleeve. The metal fixing sleeve is tightly matched with the temperature measuring rake main body.
In order to ensure that the thermocouple measuring point is positioned at the center of the shielding cover ceramic tube, preferably, one end of the shielding cover ceramic tube, which is close to the tail part of the thermocouple wire, is provided with a warp expansion section, and the outer diameter of the warp expansion section is the same as that of the metal fixing sleeve. During assembly, the thermocouple wires are fixed on the temperature measuring rake body through threads, then the shielding cover ceramic tube is installed, the metal fixing sleeve is installed, the air flow outlets of the shielding cover ceramic tube and the metal fixing sleeve are aligned with the air flow outlet of the temperature measuring rake body during installation, the thermocouple wires are fixed through hole screws, and finally the sealing cover plate is installed.
For the convenience of fixing and mounting, preferably, the metal fixing sleeve is fixedly connected with the ceramic tube of the shielding cover through a through hole screw arranged on the air outlet.
In order to avoid the metal fixing sleeve from being ablated by high-temperature air flow, the air inlet is preferably 0.3-0.5 mm lower than the top opening. The metal fixing sleeve is made of stainless steel.
The invention has the beneficial effects that:
The device for measuring the total temperature of the combustion chamber of the aeroengine can obtain the temperature distribution of the combustion chamber, has the advantages of large temperature measuring range, high temperature measuring precision, long continuous temperature measuring time, compact structure, small size, easy replacement of a thermocouple probe and low temperature measuring cost.
Drawings
Fig. 1 is a schematic structural view of an aero-engine combustion chamber total temperature measuring device of the invention.
Fig. 2 is a schematic cross-sectional structural view of the total temperature measuring device of the combustion chamber of the aero-engine.
Fig. 3 is a schematic structural view of the cooling water inlet pipe of the present invention.
Fig. 4 is a schematic structural view of the thermocouple probe according to the present invention.
Fig. 5 is a schematic structural view of the stainless steel fixing sleeve of the present invention.
Fig. 6 is a schematic structural view of a ceramic tube of the shield of the present invention.
FIG. 7 is a graph of partial measurement results of partial station temperature response measured using the apparatus of the present invention.
Detailed Description
In order that the manner in which the invention is attained and its advantages, i.e. the manner in which it is obtained, the nature of the operations and the manner in which it is utilized, a further description of the invention is provided.
As shown in fig. 1 to 6, the total temperature measuring device for the combustion chamber of the aeroengine of the present embodiment includes a mounting base 1, a temperature measuring rake body 2, a plurality of thermocouple probes 3, a cooling water inlet pipe 4, a cooling cavity 5, a cooling water outlet pipe 6, a back sealing cover plate 7, a sealing gasket 8 and a thermocouple wire outlet pipe 9.
The total temperature of the combustion chamber of the tested aeroengine is up to 1800 ℃, the air flow speed is high, the test time is up to 60s, in order to ensure the strength of the temperature measuring rake, the material of the main body 2 of the temperature measuring rake adopts high-temperature alloy (1 Cr25Ni20Si 2), and meanwhile, a cooling cavity 5 is arranged in the temperature measuring rake to cool the main body 2 of the temperature measuring rake.
The temperature in the aeroengine combustion chamber that surveys is inhomogeneous, and the temperature near the center is high, in order to reach better cooling effect, and cooling water inlet tube 4 lets in the top of temperature measurement harrow main part 2, and cooling water temperature is low this moment, and the temperature of top harrow body is high, has promoted the heat transfer, absorbs the cooling water of harrow body heat and flows through cooling chamber 5 and discharge in cooling water outlet pipe 6 department.
In order to ensure enough cooling water flow, under the condition that the diameter of the cooling water pipe is fixed, the inlet pressure of the cooling water pipe is increased, and the inlet pressure of the cooling water outlet pipe 6 is 0.8MPa.
In order to obtain the temperature distribution in the combustion chamber of the aeroengine, a plurality of thermocouple probes 3 are arranged on a temperature measuring rake, the number of the probes is determined according to the diameter of a flow passage, the diameter of the measured flow passage is 700mm, 5 probes are arranged, the positions of the probes are arranged according to equal areas, and the positions of the probes are numbered as V, IV, III, II and I in sequence from the top.
In order to reduce radiation errors and improve the measurement accuracy of the total temperature of incoming flow, the thermocouple probe 3 comprises a thermocouple wire 301, a shield ceramic tube 302, a stainless steel fixing sleeve 303, an air flow inlet 304, an air outlet 305 and mounting threads 306. The diameter of the air flow inlet 304 is 3mm, the air outlets 306 are distributed on two sides of the temperature measuring rake body 2, the diameter is 1.5mm, and the inlet-outlet area ratio is2, so that the speed error is reduced.
Because of the high incoming flow temperature, in order to reduce radiation errors, a shield ceramic tube 302 is provided, which is resistant to high temperatures on the one hand and low emissivity on the other hand. In order to reduce the radiative heat transfer between the thermocouple wires 301 and the shield ceramic tube 302, the temperature of the thermocouple is close to the temperature of the ceramic tube, which reduces the heat conduction from the ceramic tube to the temperature sensing rake body. The stainless steel fixing sleeve 303 is tightly matched with the temperature measuring rake body 2, and a gap of 0.2mm is formed between the stainless steel fixing sleeve and the shielding cover ceramic tube 302.
As the total temperature of the combustion chamber of the aero-engine is up to 1800 ℃ and is an aerobic environment, the thermocouple adopts platinum-rhodium 30-platinum-rhodium 6, and the diameter of the thermocouple wire is 0.3mm. The thermocouple is vulnerable in consideration of the high temperature state. In order to reduce the temperature measurement cost, the thermocouple wire 301 is fixed on the temperature measurement rake body through threads, and the thermocouple wire 301 can be replaced independently by disassembling the back sealing cover plate 7. Therefore, when a certain thermocouple on the temperature measuring rake is damaged, the thermocouple is replaced to ensure the recycling of the main body of the temperature measuring rake, so that the temperature measuring cost is reduced.
The tested aeroengine combustion chamber is compact in structure, the space for installing the temperature measuring rake is small, meanwhile, in order to reduce the interference of the temperature measuring rake to a flow field, the size of the temperature measuring rake is required to be small, the width of the temperature measuring rake main body 2 is 15.8mm, the height is 38mm, the width of the installation base 1 is 16mm, the height is 40mm, and the installation requirement is met under the condition of ensuring cooling.
In order to reduce the impact of high-speed gas on the temperature measuring rake and further reduce the interference of the temperature measuring rake on a flow field, the main body 2 of the temperature measuring rake is opposite to the incoming flow direction and is arc-shaped.
In order to realize the sealing of the cooling cavity 5, the thermocouple wire 301 is convenient to replace, the temperature measuring rake body 2 is rectangular in back to back flow direction, the back sealing cover plate 7 and the sealing gasket 8 are fixed on the temperature measuring rake body 2 through screws to seal the cooling cavity 5, and the middle sealing gasket is a polished copper gasket with the thickness of 0.3mm.
In order to ensure that the thermocouple measurement point is positioned at the center of the shielding cover ceramic tube, the bottom of the shielding cover ceramic tube 302 is provided with a warp expansion section, and the warp expansion section has the same outer diameter as the stainless steel fixing sleeve 303. During assembly, the thermocouple wires 301 are fixed at the lower part of the mounting hole of the temperature measuring rake body 2 through mounting threads 306, then the shielding cover ceramic tube 302 is mounted, then the stainless steel fixing sleeve 303 is mounted, the air flow outlets of the shielding cover ceramic tube 302 and the stainless steel fixing sleeve 303 are aligned with the air flow outlet of the temperature measuring rake body during mounting, the thermocouple wires are fixed through hole screws, and finally the sealing cover plate is mounted.
In order to avoid the stainless steel fixed sleeve 303 from being ablated by high-temperature air flow, the air flow inlet 304 is lower than the arc top of the temperature measuring rake facing the incoming flow direction by 0.5mm.
The total temperature measuring device of the aeroengine combustion chamber of the embodiment is fixed in a flow passage of the aeroengine combustion chamber of a certain model through the mounting base 1, the temperature in the combustion chamber is measured, the test result of the temperature response part of measuring points is shown in fig. 7, and the response time of the thermocouple can be seen to be in millisecond level. After the temperature of the measuring point III is stabilized, the average temperature reaches 2058K, the temperatures of the measuring point II and the measuring point III are compared, the temperature in the combustion chamber is obviously uneven, and the measuring result has important guiding significance on the structural design of the subsequent combustion chamber.
Claims (3)
1. An aeroengine combustion chamber total temperature measurement device, comprising:
A mounting base;
the temperature measuring rake body is of a strip-shaped structure, one end of the temperature measuring rake body is connected with the mounting base, a plurality of mounting holes with top openings facing the incoming flow direction are formed in the length direction, and a water cooling unit is arranged in the temperature measuring rake body; a plurality of thermocouple probes mounted in the corresponding mounting holes;
Thermocouple wire eduction pipe installs be used for installing the thermocouple wire of connecting thermocouple probe on the mounting base, its characterized in that, thermocouple probe includes:
The metal fixing sleeve is fixedly connected with the mounting hole;
The shielding cover ceramic tube is arranged in the metal fixing sleeve and is provided with an air inlet which faces to the top opening and an air outlet which is vertical to the incoming flow direction, and the air outlet is communicated to the outside of the temperature measuring rake main body; a gap of 0.2 mm-0.3 mm is formed between the shielding cover ceramic tube and the metal fixing sleeve; the metal fixing sleeve is tightly matched with the temperature measuring rake main body; in order to ensure that the thermocouple measuring point is positioned at the center of the shielding cover ceramic tube, one end of the shielding cover ceramic tube, which is close to the tail part of the thermocouple wire, is provided with a warp expansion section, and the outer diameter of the warp expansion section is the same as that of the metal fixing sleeve; during assembly, the thermocouple wires are fixed on the temperature measuring rake main body through threads, then the shielding cover ceramic tube is installed, the metal fixing sleeve is installed, the air flow outlets of the shielding cover ceramic tube and the metal fixing sleeve are aligned with the air flow outlet of the temperature measuring rake main body during installation, the thermocouple wires are fixed through hole screws, and finally the sealing cover plate is installed; in order to avoid the metal fixing sleeve from being ablated by high-temperature air flow, the air inlet is 0.3-0.5 mm lower than the top opening; the metal fixing sleeve is made of stainless steel;
The tail part of the thermocouple wire is in threaded connection with the bottom opening of the mounting hole, and the head part of the thermocouple wire is arranged in the ceramic tube of the shielding cover; during assembly, the thermocouple wires are fixed on the temperature measuring rake main body through threads, then a shielding cover ceramic tube is installed, and then a metal fixing sleeve is installed;
The water-cooling unit includes:
the cooling cavity is a cavity body of the temperature measuring rake body, which is opposite to the flowing direction, extends from the end close to the mounting base to the other end and is provided with a mounting opening;
a back seal cover plate sealing the mounting opening;
one end of the cooling water inlet pipe is arranged on the mounting base, and the other end of the cooling water inlet pipe extends into the cooling cavity and extends to the end far away from the mounting base;
One end of the cooling water outlet pipe is arranged on the mounting base and is communicated with the cooling cavity;
The width of the cross section of the temperature measuring rake body in the vertical incoming flow direction is 12 mm-18 mm, and the height of the cross section of the temperature measuring rake body in the incoming flow direction is 35 mm-40 mm; the side surface of the temperature measuring rake main body facing the incoming flow direction is convex arc-shaped; in order to realize the sealing of cooling cavity, be convenient for the change of thermocouple simultaneously, temperature measurement harrow back is the rectangle to the incoming flow direction, and back seal apron and sealed pad pass through the screw fixation on temperature measurement harrow main part, and sealed pad is the copper gasket of polishing, thickness 0.3~0.5 mm.
2. The aircraft engine combustor total temperature measurement device of claim 1, wherein the temperature sensing rake body is comprised of a superalloy.
3. The aircraft engine combustor total temperature measurement device of claim 1, wherein a bottom opening of the mounting hole communicates to a cooling cavity.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811252761.0A CN109341883B (en) | 2018-10-25 | 2018-10-25 | Total temperature measuring device for aero-engine combustion chamber |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811252761.0A CN109341883B (en) | 2018-10-25 | 2018-10-25 | Total temperature measuring device for aero-engine combustion chamber |
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| CN109341883A CN109341883A (en) | 2019-02-15 |
| CN109341883B true CN109341883B (en) | 2024-08-06 |
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| CN201811252761.0A Active CN109341883B (en) | 2018-10-25 | 2018-10-25 | Total temperature measuring device for aero-engine combustion chamber |
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| CN113188155A (en) * | 2021-05-07 | 2021-07-30 | 南京航空航天大学 | Backflow combustion chamber for wall temperature distribution measurement based on thermocouple |
| CN113739939A (en) * | 2021-08-31 | 2021-12-03 | 中国航发贵阳发动机设计研究所 | Total temperature probe for outlet of combustion chamber |
| CN113588105A (en) * | 2021-08-31 | 2021-11-02 | 中国航发贵阳发动机设计研究所 | High guide vane type total temperature probe structure |
| CN114136479B (en) * | 2021-10-20 | 2023-06-13 | 中国航发四川燃气涡轮研究院 | Optical-mechanical structure for measuring outlet temperature distribution of combustion chamber |
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| CN116046195B (en) * | 2023-04-03 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Movable type aeroengine wheel disk temperature measuring device |
| CN117906902A (en) * | 2024-03-19 | 2024-04-19 | 中国航空工业集团公司沈阳空气动力研究所 | Pre-heating total temperature probe and high-temperature high-Mach number airflow total temperature measurement method |
| CN118190192A (en) * | 2024-05-13 | 2024-06-14 | 中国航空工业集团公司沈阳空气动力研究所 | High-precision wide-range wind tunnel temperature field measuring device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US4747700A (en) * | 1987-06-19 | 1988-05-31 | Teledyne Industries, Inc. | Thermocouple rake |
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| CN205719306U (en) * | 2016-04-18 | 2016-11-23 | 绵阳市长力科技有限公司 | A kind of 5 stagnation temperature probes of aero-engine |
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2018
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| CN204373801U (en) * | 2014-12-10 | 2015-06-03 | 中国科学院工程热物理研究所 | A kind of high temperature liquid cooling temperature measuring equipment |
| CN209148167U (en) * | 2018-10-25 | 2019-07-23 | 浙江大学 | A kind of total temperature measurement device in aeroengine combustor buring room |
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